Abstract: An air vehicle control system utilizing variable incidence aerodynamic control surfaces deployed from within the missile body and locked in place. Only two control surfaces (instead of the four usually required for a missile which maneuvers in three dimensions) are required. The number of control surfaces required is reduced by utilizing missile roll to achieve control in any direction. Flight control of the air vehicle is achieved by a single pair of aerodynamic control surfaces located forward of the missile center of gravity. In order to produce a turning moment in any direction, the missile is rolled at a predetermined number of revolutions per second. The control surfaces are operated during the proper portion of each missile revolution to achieve the desired directional control.